GB1578822A - Missiles - Google Patents

Description

(54) IMPROVEMENTS RELATING TO MISSILES.

(71) We, RHEINMETALL Gesellschaft mit beschrinkter Haftung, of Ulmenstrasse 125,4 DUSSELDORF 1, German Federal Republic, a Company organised and existing under the laws of the German Federal Republic, 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 state ment: - This invention relates to missiles both selfpropelled and passive such as shells. Missiles vary in form according to purpose and function and in addition there are differences resulting from the various firing devices used which may include, in the case of barrel-fired weapons, the calibre and the type of barrel (rifled or smooth) and the distinction drawn between muzzle and breech loading.Selfpropelled missiles also have to be adapted according to differences as regards the selflaunching capacity and controllability as well as the necessary launching appliance required.

The variety of types of missiles affects both the production and supply especially with allied forces as limits are set on national and international standardization. The existence of numerous different types of missiles is costly.

This invention seeks to avoid or reduce these disadvantages. According to this invention there is provided a missile system comprising, in combination, a nose unit; a warhead or other payload adapted to be introduced and retained in the nose unit; and a plurality of other units of construction different from one another according to different modes of delivery of the nose unit to a target and being selectively exchangeably detachably connectible to the rear of the nose unit to form there with missiles of different construction.

This has the advantageous result that various missiles can be assembled or converted from one type to the other to render same usable for other purposes. This leads to simplification in production and supply and reduces cost with an increase in the striking power of forces.

With known ammunition using both standard and special projectiles the same weights and ranges or given calibres are provided. A compromise must therefore be found between range and payload, and this may prove to be a disadvantage.

In contrast the invention enables either the range or the payload, as desired, to be optimized in a sample manner. Furthermore, the invention provides the advantage of reducing the large variety of launching means in current use.

It is possible to have alterations to the payloads or types carried out by the combatants under field conditions.

The invention is further described and explained in conjunction with the accompanying drawing showing examples of missiles and the system.

As shown in the drawing a basic nose unit 1 is used for all the missiles Al to A7 shown, this comprising a single warhead of variable payload.

By "variable payload" is meant that different payloads both for practise and for combat purposes can be introduced into the casing of the unit 1.

A missile unit shown in Al has the basic unit 1 arranged to be fired as a projectile from field guns, anti-tank guns, howitzers or breech loading mortars of the same calibre with sealing disc B as a tail unit being detachably connected with the base of the unit. The disc B1 has a passage 2 and a sealing or guide mean 3. The passage 2 is coupled at one end to a breech element B2.

The complete missile A1 is designed to be fired from rifled barrels using spin stabilization.

If a unit 1 is to be fired from a smooth or rifled barrel with fin stabilization a missile A2 is used with a control fin system B3 positioned between the basic element 1 and the sealing disc B1. The system B3 has a central passage 4 and a number of extensible blade-like fins 5.

To enable the missile to be fired from rifled barrels the sealing or guide means 3 is arranged to rotate.

If the unit is to be subject to further acceleration during flight the missile A3 is used. Between the warhead and the control surface unit B3of the missile unit A2 a drive unit B4 is provided. In addition, the breech element B2 at the rear end of the passage 2 of the sealing unit Blis omitted. To enable the missile to be fired from rifled barrels the sealing or guide means 3 is able to rotate.

When connection is made to a rocket motor B5 the missile A4 can be launched from a rocket launcher.

To enable the missile to be fired from breech loading mortars having a smooth barrel the missile takes the form As. This results from the missile A2 , having a propulsive charge insert B6 at the rear end of the unit B1 . The propulsive charge insert B6 could also be provided at the rear end of the unit B1 of the missile A3, thus providing a further missile (not shown) for breech loading mortars having smooth barrels.

In the case of missile A6, to be fired from a firing apparatus of large calibre, the warhead unit 1 is provided with a propulsion piston B8 acting as a sabot and mounted on an additional payload housing B7. The propulsion piston B8 has a sealing or guide element 6 which may take the form of a fixed guide ring or a rotatable guide sleeve. The missile A6 is thus suitable for firing both from smooth and from rifled barrels, a multi-fin control surface unit 7 is provided in a fixed position at the rear end of the housing B7 which may assist to support the missile in the barrel.

A missile A7 has a multiple warhead which includes a casing B9 serving to accommodate a number of units I and further mounting and retaining elements which are not shown in the drawing. A rocket engine Blo is connected to the casing Bg. This forms a self-launching missile suitable for firing from rocket launchers and having a multiple warhead.

The missile A6 shows a construction of a sub-calibre forum. The propulsive piston element B8 can be used separately from the additional payload housing B7, so that further forms of missiles can be assembled.

This system is charaterised by the various parts each adapted for a particular purpose and which are readily interchangeable according to particular needs arising in respect of the launching or firing device or in relation to the target, and which can be assembled to form a missile as necessary according to the requirements.

WHAT WE CLAIM IS: 1. A missile system comprising, in combination, a nose unit; a warhead or other payload adapted to be introduced and retained in the nose unit; and a plurality of other units of construction different from one another according to different modes of delivery of the nose unit to a target and being selectively exchangeably detachably conriectible to the rear of the nose unit to form therewith missiles of different construction.

2. A missile system according to Claim 1, wherein two or more of said other units are selectively connectible with each other whereby two, or more said other units may be connected with the nose unit.

3. A missile system according to Claim 1 or 2, wherein the said other units comprise: a a unit with peripheral surfaces to sealingly engage the bore of a barrel of a calibre substantially identical to that of the nose unit, b a unit with extensible fins, c a unit including a propulsive charge forming a drive for the missile, d a rocket launching and propulsion unit, e a unit with a peripheral surface to sealingly engage a bore of greater dia meter than the nose unit, and associated with rearwardly spaced guide fins to engage the bore.

4. A missile system in accordance with any preceding Claim, including a nose casing adapted to hold several nose units ahead of a selected said other unit.

5. A missile substantially as herein described and shown in any one of Figures Al to A7 of the accompanying drawings.

6. The missile system substantially as herein described and shown in Figures Alto A6 of the accompanying drawings.

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

Claims (6)

**WARNING** start of CLMS field may overlap end of DESC **. barrels the sealing or guide means 3 is arranged to rotate. If the unit is to be subject to further acceleration during flight the missile A3 is used. Between the warhead and the control surface unit B3of the missile unit A2 a drive unit B4 is provided. In addition, the breech element B2 at the rear end of the passage 2 of the sealing unit Blis omitted. To enable the missile to be fired from rifled barrels the sealing or guide means 3 is able to rotate. When connection is made to a rocket motor B5 the missile A4 can be launched from a rocket launcher. To enable the missile to be fired from breech loading mortars having a smooth barrel the missile takes the form As. This results from the missile A2 , having a propulsive charge insert B6 at the rear end of the unit B1 . The propulsive charge insert B6 could also be provided at the rear end of the unit B1 of the missile A3, thus providing a further missile (not shown) for breech loading mortars having smooth barrels. In the case of missile A6, to be fired from a firing apparatus of large calibre, the warhead unit 1 is provided with a propulsion piston B8 acting as a sabot and mounted on an additional payload housing B7. The propulsion piston B8 has a sealing or guide element 6 which may take the form of a fixed guide ring or a rotatable guide sleeve. The missile A6 is thus suitable for firing both from smooth and from rifled barrels, a multi-fin control surface unit 7 is provided in a fixed position at the rear end of the housing B7 which may assist to support the missile in the barrel. A missile A7 has a multiple warhead which includes a casing B9 serving to accommodate a number of units I and further mounting and retaining elements which are not shown in the drawing. A rocket engine Blo is connected to the casing Bg. This forms a self-launching missile suitable for firing from rocket launchers and having a multiple warhead. The missile A6 shows a construction of a sub-calibre forum. The propulsive piston element B8 can be used separately from the additional payload housing B7, so that further forms of missiles can be assembled. This system is charaterised by the various parts each adapted for a particular purpose and which are readily interchangeable according to particular needs arising in respect of the launching or firing device or in relation to the target, and which can be assembled to form a missile as necessary according to the requirements. WHAT WE CLAIM IS:

1. A missile system comprising, in combination, a nose unit; a warhead or other payload adapted to be introduced and retained in the nose unit; and a plurality of other units of construction different from one another according to different modes of delivery of the nose unit to a target and being selectively exchangeably detachably conriectible to the rear of the nose unit to form therewith missiles of different construction.

2. A missile system according to Claim 1, wherein two or more of said other units are selectively connectible with each other whereby two, or more said other units may be connected with the nose unit.

3. A missile system according to Claim 1 or 2, wherein the said other units comprise: a a unit with peripheral surfaces to sealingly engage the bore of a barrel of a calibre substantially identical to that of the nose unit, b a unit with extensible fins, c a unit including a propulsive charge forming a drive for the missile, d a rocket launching and propulsion unit, e a unit with a peripheral surface to sealingly engage a bore of greater dia meter than the nose unit, and associated with rearwardly spaced guide fins to engage the bore.

4. A missile system in accordance with any preceding Claim, including a nose casing adapted to hold several nose units ahead of a selected said other unit.

5. A missile substantially as herein described and shown in any one of Figures Al to A7 of the accompanying drawings.

6. The missile system substantially as herein described and shown in Figures Alto A6 of the accompanying drawings.