GB2154716A

GB2154716A - A spin projectile

Info

Publication number: GB2154716A
Application number: GB08502742A
Authority: GB
Inventors: Adolf Weber; Stephan Kerk; Hans Straus
Original assignee: Diehl GmbH and Co
Current assignee: Diehl Verwaltungs Stiftung
Priority date: 1984-02-04
Filing date: 1985-02-04
Publication date: 1985-09-11
Also published as: IT8519344A0; IT8520685V0; DE3403936A1; GB8502742D0; DE3403936C2; IT1183150B

Abstract

A projectile may be fired from the weapon barrel of an aircraft to make possible a camouflaging of the aircraft at a location which the aircraft will reach in a few seconds. The detonation mechanism (3, 7) of the projectile is activated by the projectile spin and detonates, upon the abatement of spin thereof, an ejection charge (17). Mounted in the projectile body are an ejection piston (18) and an inner casing (19). Casing (19) is filled with a window charge (23) and blasts off the tail (21) of the projectile upon detonation of the ejection charge (17), so that the window charge leaves the projectile body. <IMAGE>

Description

SPECIFICATION A spin projectile This invention relates to a spin projectile for firing from a weapon barrel of for example, an aircraft; the noise of the projectile will usually but not necessarily accommodate a detonating mechanism which is designed to detonate a specific distance in front of the aircraft.

It is, moreover, known to drop, for camouflage, chaff or a window (metallic strips used to interfere with radar) which misdirects a pursuing object. In this respect it tends to be disadvantageous that the misdirection practically always takes place behind the aircraft.

Camouflage in front of the aircraft does not seem to be conceivable merely by dropping chaff.

An object of an embodiment of the present invention is to provide a spin projectile to make possible a protective camouflaging for an aircraft at a location which it will reach in a relatively short time (for example a few sec onds).

In accordance with the present invention there is provided a spin projectile in which a detonation mechanism is activatable by the projectile spin and upon abatement of the spin detonates an ejection charge; an ejection piston and an inner casing are mounted in the projectile body and the inner casing is filled or provided with a window (chaff) charge and blasts off the tail (or other part) of the projectile upon detonation of the ejection charge, and the window charge then leaves the projectile body.

The spin projectile with the window charge may be fired in the same way as any other projectile, and, for example, in front of an aircraft. After a specific time, for example one second up to two seconds, the detonation mechanism detonates, so that the window charge is ejected and a screening camouflage cloud builds up in front of the aircraft.

Since, on exit from the projectile, the linear or translatory and rotary movements of the projectile are still conveyed to the window charge, a camouflage cloud which is similar to the aircraft contour will build up in front of the aircraft.

The time between firing and detonation of the projectile can be set exactly by the detonation mechanism, since the degree of abatement of the spin is a precise indicator for the flying distance covered.

The detonation mechanism is, through its mechanical construction, sturdy, reliable, safe, simple and relatively insensitive to interference or malfunction.

In a preferred development of the present invention, the detonation mechanism has a spring which loads a release lever which is swung or actuated under the effect of the spin of the projectile, and which frees a blocking segment or portion, when the spring swings or actuates the release lever contrary to the effective direction of the spin. By adjusting or setting the force of the spring, the flying time of the projectile can be set after which the window charge is ejected. As a result of this arrangement, the flying time can be determined in advance considerably more exactly than when using pyrotechnical delayed-action charges.

A further advantage of the described mechanism consists in that the detonation mechanism and the ejection charge may be arranged compactly, more particularly in the length dimension of the projectile, so that plenty of space remains in the projectile body for the window charge.

An embodiment of a spin projectile in accordance with the present invention will now be described, by way of example only, with reference to the single accompanying figure of the drawing.

Referring to the figure, a retaining body 2 is screwed into a projectile nose (or tip) 1; this fixes a destructor plate 3 in the projectile nose 1. Inserted into a cavity 4 is a firing pin carrier 6, which in the depicted rest position is held back from the destructor plate 3 against the force of compression spring 5.

The firing pin 7 projects into a perforation 8 in the retaining body 2. A release lever 9 and a blocking segment or portion 10 are swingably mounted on the destructor plate 3. The release lever 9 is loaded by a torsion spring 11. Fastened to the release lever 9 is a weight 11 (not shown in more detail) which on projectile spin swings (actuates) the release lever 9 in such a way that it engages or hooks itself with the blocking segment 10 and holds this for instance (approximately) in the position shown. The torsion spring 11 is so arranged that it counteracts the deflection of the release lever 9.

Arranged in the retaining body 2 is a bearing bush 1 2 for a rotor 1 3 which provides a pre-barrel safety. In the depicted position the rotor 1 3 is secured by means of a spring band (flat keep spring) 1 4. Arranged in the rotor 1 3 is a firing cap 1 5.

The projectile nose 1 is screwed on a projectile body 1 6. An ejection charge 1 7 is arranged in the projectile body 1 6. Following charge 17, an ejection piston 1 8 is mounted in the projectile body 1 6 and then an inner casing 1 9. A sealing ring 20 is provided on the periphery of the ejection piston 1 8. The inner casing 1 9 is divided up into two or more parts. The casing 1 9 may be split equally lengthwise (preferably) and/or transversely.

Screwed into the tail of the projectile body 16 is a tail part 21 which has a predetermined breaking location 22. The inner casing 1 9 rests against (and is received by) the tail part 21. The inner casing 1 9 is filled with aluminised plastics threads 23. Arranged on the outside of the projectile body 1 6 is a driving band 24.

The mode of operation of the described projectile is, for example, approximately as follows: If the projectile is fired, for example, in the course of a firing sequence from the automatic weapon of an aircraft, then, after leaving the weapon barrel the spring band (keep spring) 14 frees under the effect of the spin of the rotor 1 3. Rotor 1 3 now aligns itself in such a way that the firing cap 1 5 lies opposite the firing pin 7.

Simultaneously, under the effect of the spin a safety lever (not shown in more detail) frees the release lever 9, so that this release lever swings in such a way against the force of the torsion spring 11 that it hooks itself (engages) with the blocking segment 10. Thereby, the firing pin carrier 6 is further held back against the force of the compression spring 5.

In the course of flight of the projectile the spin decreaes. An instant is then reached at which the force of the torsion spring 11 is greater than the centrifugal force acting on the release lever 9. The torsion spring 11 then swings (actuates) the release lever 9, which thereby frees the blocking segment 10.

Segment 10 is now moved by the firing pin carrier 6 and the firing pin 7 strikes the firing cap 1 5. This detonates the ejection charge 1 7.

As a result of the detonation of the ejection charge 1 7 the ejection piston 1 8 is set in motion. The inner casing 1 9 is forced against the tail part 21, until the predetermined breaking location 22 thereof breaks. Under the effect of the ejection charge 1 7 the ejection piston 1 8 with the inner casing 1 9 and the aluminised plastics threads 23 is expelled.

After leaving the projectile body 16, the parts of the inner casing 1 9 separate and the aluminised plastics threads 23 are distributed into a long-drawn camouflage cloud which is spread in front of the aircraft.

Besides the tail-side ejection of the window or chaff, an ogive-side ejection is also readily possible. In such a case a base fuze, a baseside ejection charge and a hood (ballistic cap) removable from the projectile body may be provided.

Further according to the present invention there is provided a spin projectile for firing from a weapon barrel, comprising a detonation mechanism which is adapted to be activated by the spin of the projectile and once the spin of the projectile has abated to a particular value the detonation mechanism detonates an ejection charge to expel a window (chaff) charge from the projectile.

Still further according to the present invention there is provided a method of screening or camouflaging an aircraft or flying body comprising firing a projectile ahead of the aircraft or flying body to detonate generally in the flight path thereof, the projectile having a window (chaff) charge which is designed to be ejected from the projectile to produce a screen or camouflage cloud on detonation of an ejection charge on the projectile. The projectile may be a spin projectile so that the window charge is ejected from the projectile automatically by an on board detonation mechanism once the spin has abated to a particular value. More than one projectile may be fired in a particular sequence to provide the desired camouflage.

Claims

1. A spin projectile for firing from a weapon barrel of a weapon, such as an antiairacraft gun or an aircraft cannon, comprising a detonation mechanism which detonates in a time-programmed manner, in which projectile the detonation mechanism is activated by the projectile spin and upon abatement of the spin detonates an ejection charge, and, mounted in the projectile body are an ejection piston and an inner casing; the inner casing is filled or provided with a window charge and blasts off a projectile part (such as a projectile cap or projectile tail) upon detonation of the ejection charge, so that the window charge leaves the projectile body.

2. A spin projectile as claimed in Claim 1, in which the detonation mechanism has a spring means which loads a release lever which is actuated under the effect of the spin of the projectile and which frees a blocking segment or portion when the spring means actuates the release lever to move against the effective direction of the spin.

3. A spin projectile as claimed in Claim 1 or 2, in which the window charge is formed from aluminised plastics threads.

4. A spin projectile as claimed in any one of the preceding claims, in which the inner casing rests against the said projectile and said projectile part has a predetermined breaking point or location.

5. A spin projectile as claimed in any one of the preceding claims, in which the inner casing is split up into two or more parts.

6. A spin projectile for firing from a weapon barrel, comprising a detonation mechanism which is adapted to be activated by the spin of the projectile and once the spin of the projectile has abated to a particular value to the detonation mechanism detonates an ejection charge to expel a window (chaff) charge from the projectile.

7. A projectile as claimed in Claim 6 in which the detonation mechanism has a spring means which loads a release lever which is actuated under the effect of the spin of the projectile and which frees a blocking segment or portion when the spring means actuates the release lever to move against the effective direction of the spin.

8. A method of screening or camouflaging an aircraft or flying body comprising firing a projectile ahead of the aircraft or flying body to detonate generally in the flight path thereof, the projectile having a window (chaff) charge which is designed to be ejected from the projectile to produce a screen or camouflage cloud on detonation of an ejection charge on the projectile.

9. A spin projectile substantially as herein described with reference to the accompanying drawing.

1 0. A method as claimed in Claim 8 and substantially as herein described with reference to the accompanying drawing.