DE3631277C1 - Empennage (set of control surfaces) for missiles - Google Patents

Abstract

The invention relates to an empennage for missiles, which is constructed separately from the missile such that it can be pushed onto the firing tube and is automatically connected to the missile during firing, so that the missile has an empennage which is already completely stabilised at the moment when it leaves the firing tube. <IMAGE>

Description

The invention relates to a tail unit for missiles according to the Generic term of claim 1. DE-OS 34 08 585 is a such a missile tail known. This embodiment however, requires considerable manufacturing effort for integration in the missile.

The US-PS 40 24 998 is a tail unit for a launchable missile become known, at the front and rear end of each floor arranged a locking ring and between them a tail boom ring is slidably mounted. Using locking notches and locking pins the tail boom ring is now at the front or rear of the Missile positioned. For the storage and transportation of such Missile, however, this design is unfavorable because either must the missiles and tail units are brought separately to the site if or both are assembled beforehand, then the required one Cargo capacity severely limited due to the fixed tail assembly.

The object of the present invention is to overcome these disadvantages to eliminate and to create a tail unit of the type mentioned at the beginning, that a much higher functional reliability and flight accuracy of the Made missiles possible and improved their range and performance.

This object is achieved by the measures outlined in claim 1 solved. The fact that the missile is no longer with a tail assembly must be conceived, the one previously taken up by it Space in and on the missile free, so that once the volume for the shaped charge is increased, which leads to an increase in performance and for the second time there will be more space for rocket propulsion created the  leads to an extension of the range. The aforementioned Flight accuracy is improved in that the previous Frequently occurring exit errors due to imprecise and asymmetrical extension of the tail units are eliminated and functional safety is increased because the tail wings already extended and locked before the launch are so that the missile immediately at Leaving the launch tube by a fully "extended" Tail is stabilized.

Advantageous refinements are in the subclaims is specified and in the description below an embodiment explained and in the figures the drawing schematically outlined. It shows

Fig. 1 shows an embodiment of a tail unit arranged on the launch tube with the missile inserted, the upper half of the cross-section showing the retracted tail unit and the lower half the extended position;

Fig. 2 shows a cross section in a schematic representation of the rear projectile or missile end with the tail unit accrued at its cone immediately after the launch.

As can be seen from FIG. 1, the missile 10 is in the launch tube 11 in the rest or transport position and rests with its end face against the so-called sabot 18 . The tip of the missile 10 is covered and protected with a protective hood 17 . The tail boom ring 12 is arranged between the protective hood and the launch tube in such a way that it receives the protective hood as a centering and forms the front guide of the missile 10 during the launch. The rear guidance takes place via the sabot 18 and through the launch tube 11 . The empennage wings are carried by the empennage carrier ring 12 . The centering ring 12 c of the tail boom ring 12 engages over the launch tube surface and is fastened to it by shear pins 15 .

The inner surface of the tail boom ring 12 is correspondingly conical with the cone 10 a of the end part of the missile 10 .

Furthermore, it can be seen from FIG. 1 that the empennage wings 13 either lie backwards in the folded state and are held by displaceable or foldable wing holders 16 or are folded forward and are then held by elements of the protective hood (these elements are not in the drawing) shown). By pulling off the protective hood, the guide surfaces are automatically brought into the active position. For this purpose, a torsion spring 13 a is arranged in each case, which in the folded state always holds the guide surface under prestress. Furthermore, a lock 14 is arranged which holds these guide surfaces in the flight position. Of course, the guide surfaces of the carrier ring can also be rigid and therefore always remain in the extended position. This is a storage and transportation problem, but also a cost factor. If the tail boom rings and launch tubes are to be stored and transported separately, the rigid extended embodiment is more advantageous because the carrier rings can be stacked on top of one another.

However, the assembly must then be carried out on site will. However, the weapon should be ready to fire Condition stored and transported, is clear prefer the collapsible conception what then, however, through the aforementioned additional Construction and design measures is more expensive.

Due to the proposed tail boom ring and its arrangement on or on the launch tube of the missile, at the same time this ring still serves as a front floor guide, an embodiment has now been created in which the tail unit is only automatically connected to the missile when it leaves the launch tube Has. This moment after the launch is shown in FIG. 2. The missile begins its flight with the tail fully extended, so its position is fully stabilized from the first moment.

Claims (6)

1. tail unit for missiles which are launched from launch tubes, the tail wings are in the unfolded state when leaving the launch tube, characterized in that the tail unit ring ( 12 ) is arranged separately from the missile ( 10 ) on the end tube ( 11 ) so that it automatically from shot missile ( 10 ) is taken and positively connected to it. 2. tail unit according to claim 1, characterized in that the tail wings ( 13 ) on the tail boom ring ( 12 ) are rotatably mounted and held in the folded state under the bias of a torsion spring ( 13 a ) of wing holders ( 16 ) of the launch tube ( 11 ). 3. empennage according to claims 1 or 2, characterized in that the empennage wings ( 13 ) are held in the folded state under pretension by the protective hood ( 17 ) of the launch tube ( 11 ). 4. tail unit according to claims 1-3, characterized in that the tail boom ring ( 12 ) by means of shear pins ( 15 ) or other holding elements on the launch tube ( 11 ) is attached. 5. tail unit according to claims 1-4, characterized in that the tail unit ring ( 12 ) is formed at its front end in the direction of flight as a centering ( 12 b ) for the protective hood ( 17 ). 6. tail unit according to claims 1-5, characterized in that the wing holder ( 16 ) rigid or displaceable, possibly rotatably attached to the launch tube ( 11 ).