GB1605399A - Improvements in launching arrangements for rocket-propelled missiles - Google Patents

Description

(54) IMPROVEMENTS IN LAUNCHING ARRANGEMENTS FOR ROCKET-PROPELLED MISSSILES (71) We, SHORT BROTHERS & BR< HARLAND LIMITED, a Northern Ireland Company of Airport Road, Belfast, Northern Ireland, 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 launching arrangements for rocket-propelled missiles and is particularly though not exclusively concerned with a launcher for a missile required to be fired into the air at a target such as an aircraft.

In our co-pending British patent application No. 7298/63, (Specification No 1605400) there is described a missile which is eminently suitable for use by armed land forces against attacks by aircraft flying at low level. A launcher for the missile is required which can easily be carried by one man and held by him during firing of the missile so that he can direct the missile against an approaching aircraft.

The launcher conveniently consists 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 laner may be directed by the operator toward the target and the missile rocket motor fired so that the missile is ejected forwardly out of the tube at high speed.

The launcher tube is of slightly larger diameter than the main body of the missile and is provided with a large square flange which is arranged at the forward end of the tube and to which is fitted a large cover or cap of pyramidal form for protecting the nose of the missile projecting from the forward end of the tube. The launcher so formed is intended to provide protection for the missile during transportation, the protective cover or cap being removed just prior to firing. It will howeverbe appreciated that while the other end of the tube requires to be open during firing the rear end of the missile needs to be protected against the ingress of dust and moisture during transportation and storage.

It is an object of the present invention to provide an improved launching arrangement which will meet this requirement.

According to the present invention there is provided a launching arrangement for a rocket propelled missile comprising a missile launching tube housing a missile which upon firing is ejected from the forward end of the tube, and a blow-out panel which protects rear end of the missile against the ingress of moisture and dust in transportation, which panel is secured by securing means to the rear end of the missile and which is held from rearward movement relative to the missile solely by said securing means when the missile is ready to be fired from the tube, the arrangement being such that upon the firing of the missile the securing means give way under the rearward thrust from the gases of the missile motor and the panel is blown from the rear end of the tube.

The blow-out panel is preferably secured to the rear end of the missile by screws the threads of which shear when the panel is subjected to the thrust from the rocket motor.

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 of a missile launching arrangement according to the invention with the missile housed in its launching tube in a position for transportation and in readiness for firing, Fig. 2 is a part sectional side elevation of the launching arrangement shown in Fig 1 illustrating the missile on its flight from the tube, Fig. 3 is a broken part-sectional side elevation of the rear end of the missile shown in Fig 1, drawn to a larger scale, with the section taken on the line III-III in Fig. 4, Fig. 4 is a rear view of the missile shown in Fig. 3, with a blow-out panel secured to the rear end of the missile, Fig. 5 is a rear view of the missile shown in Fig. 3, with the blow-out panel removed, Fig. 6 is a cross-section of the missile shown in Fig. 3, taken on the line VI - VI in Fig. 3, Fig. 7 is a cross-section of the missile shown in Fig. 3, taken on the line VII - VII in Fig. 3.

Fig. 8 is a cross-section of the missile shown in Fig. 4, taken on the line VIII - VIII in Fig. 4, Fig. 9 is a broken section of the missile shown in Fig. 4 taken on the line IX - tX in Fig. 4, Fig. 10 is a part sectional side elevation of the rear end of the arrangement shown in Fig. 1 with the rear end of the missile protruding from the rear end of the launching tube during an initial stage of assembly, Fig. 11 is a cross-sectional broken end elevation of the arrangement shown in Fig. 10 drawn to a larger scale, the section being taken on the lineXl-XI in Fig. 10, Fig. 12 is a broken sectional side elevation of a portion of the rear end of the missile and launching tube shown in Fig. 10 during the initial stage of assembly, the section being taken on the line XII - XII in Fig. 11, and Fig. 13 is a view similar to that shown in Fig.

12, illustrating the missile in a final stage of assembly in a position for transportation and in readiness for firing as shown in Fig 1.

Referring first to Figs. 1 and 2, 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 numberal 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 and the main body portion 12 of the missile also houses an explosive charge and detonating mechanism as well as a starting rocket motor and a main rocket motor hereinafter to be more fully described.

Upon the main body portion 12 of the missile is arranged a metal sleeve 17 which can freely slide along the body portion 12 and is provided with four equiangularly spaced radially projecting fins 18 welded to the sleeve 17.

A launcher 19 is provided comprising a launching tube 20, and in a preferred embodiment of the invention the tube 20 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 handle control bar mounted on the launching tube 20 and by means of which he can direct the tube 20 at the required angle of elevation and by turning round with the launcher follow a target.

The missile is mounted in the launching tube 20 as hereinafter to be described in more detail, by bringing the sleeve 17 carrying the stabilising fins 18 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 20, the sleeve 17 being held forward of the launcher tube 20 with the fins 18 resting against a flange 2] carried on the forward end of the tube 20 and the main body portion 12 of the missile housed in the tube 20 in the position shown in Fig. 1.

During transportation and storage the forward end of the missile 11 is protected by a pyramidal cap or cover (not shown) which fits over the nose portion 13 and the sleeve 17 with its stabilising fins 18 and which is secured to the flange 21. In preparation for firing of the missile the protective cap is removed.

The missile 11 when fired is propelled forwardly in the tube 20 and ejected from the forward end thereof at high speed. The sleeve 17 carrying the stabilising fins 18, being free on the main body portion 12 of the missile is almost instantaneously brought to the rear end of the missile 11 as the latter leaves the end of the tube 20, as shown in Fig. 2, the rear terminal portion of the sleeve 17 riding up on to a circumferential enlargement 22 at the rear of the main body portion 12 of the missile. The arrangement of the sliding sleeve with its stabilising fins is the subject of our copending British patent application No. 47041/64 (Specification No 1605397).

The starting rocket motor and the main rocket motor hereinbefore referred to are housed at the rear end of the missile and reference will now be made to Figs. 3 to 9 which illustrate the arrangement of the two motors. The starting motor comprises a plurality of solid rocket fuel charges 23 to 26 arranged in an annular housing 27 concentric with the longitudinal axis of the missile and at the rear end thereof, each charge extending longitudinally with respect to the missile and communicating at its rear end with discharge nozzles 28 having exits in an annular end face 29 of the missile.The charges 23 to 26 are circumferentially spaced within the annular housing 27, one of the spaces between adjacent charges containing a primer 30 shown in Figs. 3 and 6, the foremost end of which is adjacent an igniter 31 for igniting the individual charges 23 to 26 of the starting motor. and the other three spaces between adjacent charges containing pyrotechnic flares 33 each of which is provided at its rear end with a flare igniter 34.

The main rocket motor of the missile is arranged forwardly of the starting motor and comprises an annular solid fuel charge 35 arranged concentrically with respect to the missile axis, and a central discharge duct 36 bounded by the starter motor housing 27 is provided for discharging from the rear end of the missile the gases from the main motor.

The starting motor is initially fired when the missile is in its launching tube so as to impart a considerable thrust to the missile to eject it from the tube, the life of the starting motor being sufficiently short that it is expended by the time the missile leaves the tube, and a time delay mechanism is employed for delaying the firing of the main rocket motor so that the main motor is fired only when the missile is at a safe distance from the launching personnel. The three pyrotechnic flares 33 are ignited when the main motor is fired, the gases developed thereby giving rise to combustion of the igniters 34 arranged in the exit of the main duct 36.

As will be seen in Fig. 5, the rear end of the missile presents a large central outlet for the duct 36 of the main rocket motor and a plurality of small outlets for the starting motor nozzles arranged in the annular end face 29. The outer casing 38 of the rear end of the missile extends rearwardly of the annular end face 29 to form a short skirt portion and in accordance with the present invention there is provided a circular blow-out panel 39 which is arranged to engage as a sliding fit in the skirt portion and bear against the annular end face 29, thereby preventing dust and moisture from entering the rear end of the missile. The panel 39 is secured to the end face by screws 40 and 41 which pass through the panel 39 and are screwed into the end face 29, and the threads of the screws are such that they will shear under a predetermined low load on the panel.

In operation, upon the firing of the starting motor the blow-out panel 39 is subjected to a considerable rearward thrust from the gases developed in the nozzles 28, with the result that the screws 40, 41 holding it in place on the rear end face 29 are sheared and the panel is ejected rearwardly from the missile and out of the rear end of the launching tube 20, the missile. the missile thrust reacting against the panel 39 and not against the launching tube 20.

It will be appreciated that means should be provided for preventing the missile from falling out of its launching tube during transportation and a device for this purpose will now be described with reference to Figs. 10 to 13.

Referring first to Fig. 10, the missile 11 is inserted with its rear end first into the forward end of the launching tube 20 and moved rearwardly to a position in which the rear end of the missile projects from the rear end of the launching tube as shown in Fig. 10. The blow-out panel 39 is then fitted into the outer casing 38, as best seen in Fig. 12, and secured in place as hereinbefore described by screws 40 and 41. The panel 39 so positioned leaves a circumferential recess 42 between the end of the casing 38 and a shoulder on the panel and a pair of retaining spring clips 43 are fitted into the recess in diametrically opposed relation. As shown in Fig. 11, each of the spring clips 43 is provided with a central projecting portion 44 which normally projects beyond the surface of the outer casing 38 when the clip is in a relaxed condition.

A pair of locating holes 45 are provided in the rear end of the launching tube 20 at diametrically opposed positions and in carrying out the final stage of the assembly of the missile in the tube 20 the missile is pushed forward in the tube from the position shown in Fig. 12 with the spring clips 43 manually depressed so as to pass within the tube 20 until a position is reached in which the projections 44 spring up into the locating holes 45 as shown in Fig. 13. With the retaining clips 43 so positioned the missile is prevented from moving forwardly or rearwardly in the tube 20, except upon firing when the missile moves forwardly and the blow out panel 39 is ejected rearwardly.

WHAT WE CLAIM IS: 1. A launching arrangement for a rocket propelled missile comprising a missile launching tube housing a missile which upon firing is ejected from the forward end of the tube, and a blowout panel which protects the rear end of the missile against the ingress of moisture and dust in transportation, which panel is secured by securing means to the rear end of the missile and which is held from rearward movement relative to the missile solely by said securing means when the missile is ready to be fired from the tube, the arrangement being such that upon the firing of the missile the securing means give way under the rearward thrust from the gases of the missile motor and the panel is blown from the rear end of the tube.

2. An arrangement according to claim 1, wherein the blow-out panel is secured by screws the threads of which shear when the panel is subjected to the rearward thrust of the gases developed by the rocket motor of the missile.

3. An arrangement according to claim 2, wherein the rear end of the missile to which the panel is fitted presents a large central outlet for the gases from the main rocket motor and a plurality of smaller outlets for the gases from a starting rocket motor, the smaller outlets being arranged in an annular end face of the missile surrounding the central outlet and the panel being secured to said end face and serving to cover the central outlet and the annular end face.

4. An arrangement according to claim 3, wherein the casing of the missile extends rearwardly of the annular end face to form a skirt portion and the blow-out panel is arranged as a sliding fit in the skirt portion.

5. A launching arrangement for a rocket-propelled missile substantially as hereinbefore described with reference to the accompanying drawings.

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

Claims (5)

**WARNING** start of CLMS field may overlap end of DESC **. As will be seen in Fig. 5, the rear end of the missile presents a large central outlet for the duct 36 of the main rocket motor and a plurality of small outlets for the starting motor nozzles arranged in the annular end face 29. The outer casing 38 of the rear end of the missile extends rearwardly of the annular end face 29 to form a short skirt portion and in accordance with the present invention there is provided a circular blow-out panel 39 which is arranged to engage as a sliding fit in the skirt portion and bear against the annular end face 29, thereby preventing dust and moisture from entering the rear end of the missile. The panel 39 is secured to the end face by screws 40 and 41 which pass through the panel 39 and are screwed into the end face 29, and the threads of the screws are such that they will shear under a predetermined low load on the panel. In operation, upon the firing of the starting motor the blow-out panel 39 is subjected to a considerable rearward thrust from the gases developed in the nozzles 28, with the result that the screws 40, 41 holding it in place on the rear end face 29 are sheared and the panel is ejected rearwardly from the missile and out of the rear end of the launching tube 20, the missile. the missile thrust reacting against the panel 39 and not against the launching tube 20. It will be appreciated that means should be provided for preventing the missile from falling out of its launching tube during transportation and a device for this purpose will now be described with reference to Figs. 10 to 13. Referring first to Fig. 10, the missile 11 is inserted with its rear end first into the forward end of the launching tube 20 and moved rearwardly to a position in which the rear end of the missile projects from the rear end of the launching tube as shown in Fig. 10. The blow-out panel 39 is then fitted into the outer casing 38, as best seen in Fig. 12, and secured in place as hereinbefore described by screws 40 and 41. The panel 39 so positioned leaves a circumferential recess 42 between the end of the casing 38 and a shoulder on the panel and a pair of retaining spring clips 43 are fitted into the recess in diametrically opposed relation. As shown in Fig. 11, each of the spring clips 43 is provided with a central projecting portion 44 which normally projects beyond the surface of the outer casing 38 when the clip is in a relaxed condition. A pair of locating holes 45 are provided in the rear end of the launching tube 20 at diametrically opposed positions and in carrying out the final stage of the assembly of the missile in the tube 20 the missile is pushed forward in the tube from the position shown in Fig. 12 with the spring clips 43 manually depressed so as to pass within the tube 20 until a position is reached in which the projections 44 spring up into the locating holes 45 as shown in Fig. 13. With the retaining clips 43 so positioned the missile is prevented from moving forwardly or rearwardly in the tube 20, except upon firing when the missile moves forwardly and the blow out panel 39 is ejected rearwardly. WHAT WE CLAIM IS:

1. A launching arrangement for a rocket propelled missile comprising a missile launching tube housing a missile which upon firing is ejected from the forward end of the tube, and a blowout panel which protects the rear end of the missile against the ingress of moisture and dust in transportation, which panel is secured by securing means to the rear end of the missile and which is held from rearward movement relative to the missile solely by said securing means when the missile is ready to be fired from the tube, the arrangement being such that upon the firing of the missile the securing means give way under the rearward thrust from the gases of the missile motor and the panel is blown from the rear end of the tube.

2. An arrangement according to claim 1, wherein the blow-out panel is secured by screws the threads of which shear when the panel is subjected to the rearward thrust of the gases developed by the rocket motor of the missile.

3. An arrangement according to claim 2, wherein the rear end of the missile to which the panel is fitted presents a large central outlet for the gases from the main rocket motor and a plurality of smaller outlets for the gases from a starting rocket motor, the smaller outlets being arranged in an annular end face of the missile surrounding the central outlet and the panel being secured to said end face and serving to cover the central outlet and the annular end face.

4. An arrangement according to claim 3, wherein the casing of the missile extends rearwardly of the annular end face to form a skirt portion and the blow-out panel is arranged as a sliding fit in the skirt portion.

5. A launching arrangement for a rocket-propelled missile substantially as hereinbefore described with reference to the accompanying drawings.