DE2311761C2 - Guidance system for self-propelled, unguided missiles - Google Patents

Description

can be, must be so much smaller than the thickness
the swirl cam that the tail unit in every position
of the missile until it finally leaves the
Guide system freely in the twist grooves 10 and 13
can move. 5

Instead of four pipe ring pieces, a closed pipe can be used, ώ with the twist grooves milled in from the distance e in front of the
Widen the mouth accordingly.

ίο

For this purpose 2 sheets of drawings

20th

«0

45

SO

• 0

Claims (1)

1 2 works. Patent claims: In a guide system known from DE-AS 19 54 540 is the rear guide element as a guide Guidance system designed for self-propelled unguided guiding ring, while the front guidance missile, in which the missile with two in the 5 element is formed by twist cams. This has to Distance from one another arranged differently result that forfeit the rear region of the launch tube Guide elements is provided and must be narrow in order to tilt the missile Guiding system avoid the guiding surfaces for the rear and in this case the launcher can guide element as far as in front of the mouth of the guide no longer from behind, but only from the front gelarungssystems end up being the distance between the guide 10, which is considerable in the case of large missiles elements on the missile corresponds, thereby causing difficulties characterized in that the front guide- The object underlying the invention is element is a guide ring (3) and the rear Füh- stood in it, a guide system of the beginning and in the Rungs element from in swirl grooves (10) out of the twist preamble of claim described type so cams (5) and the twist grooves (10) from the ι j to form that a perfect guidance without Ab- Position (11), which corresponds to the distance (e) between the twist cams tilting the missile when leaving the guide (5) corresponds to the guide ring (3), expanded and reached the system and still the launching device from this point (11) are deepened. tion can be loaded from behind. This object is achieved according to the invention 20 with the features from the characterizing part of Claim. The inventive design of the guide The invention relates to a management system for self-rungssystetns is achieved that from the moment driven, unguided missile, in which the flight in which the guide ring drives the guidance system body with two spaced apart 25 can, the cams freely and without any differently acting guide elements verse forces are transmitted in the extended twist groove hen is and move the guide surfaces for ten in the guidance system, so that from this moment on the the rear guide element so far in front of the muzzle missile due to gravity a certain of the guidance system can end up falling through the distance of the guidance route without changing the direction corresponding elements on the body. 30 changes its longitudinal axis With unguided missiles it is important that the An embodiment of a guidance system according to The longitudinal axis of the missile when leaving the guide of the invention is shown in FIGS. 1 and 2 shown system as precisely as possible with the longitudinal axis of the F i g. 1 shows a missile in which as a front Guiding system coincides, since angular deviation- guiding one guiding ring, as rear guiding two genes between these two axes, deviations in 35 guide cams are used. the trajectory can result in the greater F i g. FIG. 2 shows that relating to the missile according to FIG. Become 1, the greater the shooting range. In order to ensure that the guidance system according to the invention
len that the axis of the missile in the guidance system The missile 1 in F i g. 1 is in the vicinity of its axis coincides with is provided with a guide ring 3 from DE-OS focus 2. 21 40 566 and DE-OS 20 30 038 known two Füh- 40 At the tail of the missile in the vicinity of the thruster 4 stanchions to be arranged at a distance from each other. In these two opposing twist cams 5 on known guide systems, however, there is not yet a ring 6 carrying these cams, which takes into account that the missile can tilt if the first guide leaves the guide device at the same time to guide and initiate the twist. to serve. To stabilize the missile after leaving, several, spaced apart guides 45 of the guidance system can be provided in a known manner in one of the tail units 7 and 8 in DE-OS 19 44152. The guidance system described as the guidance system provided. The purpose of this is in FIG. 2 schematically shown pipe 9, where it is a guided missile, however, it is assumed that this pipe consists of four pipe tubes, so that there are small deviations in the axis of the flight ring pieces. 50 are attached so that between the pipe ring pieces the chen can be and it is only necessary, Abwei- twist grooves 10 remain. V / ie from FIG. 2, it can be seen that measures to prevent a premature crash of the twist grooves 10 are extended from the point 11 on, could result in the missile. Dementspre- whereby the distance e of the point 11 from the Rohrmünchend are in this known guide system three training 12 is the distance e of the twist cam 5 from the guides provided, which is far behind the heavy 55 guide ring 3 in FIG. 1. This ensures that lie at the point of the missile, with the same radially supporting moment in which the guide ring 3 are the elements at the very back and the swirling Ab- tube mouth 12 leaves, the swirl cams 5, the tight supports are arranged further forward. These multiple sections 10 leave the twist grooves and enter the soft guide, however, not yet sufficient to ensure sections 13 enter, between the points that the longitudinal axis of the missile immediately 60 twist cams 5 and the expanded twist grooves 13 so much after leaving the guide system with the longitudinal game there is that the missile by so much durchfallen se of the guide system matches because, after can, as the height of fall during the time, in $ the front guide has left the guide system, which the twist cam 5 cover the distance e. The rear guide is still guided until this also acts, as soon as the guide ring 3 leaves the barrel mouth j the guide system and has left the guide system during this time, on the tail of the missile no more or supportive effect under the force of gravity Force on, so that the tilting effect with belayer strong tilting movement of the missile occurs is avoided. The thickness of the tail units 7 and 8, which can have a negative impact on accuracy, as a rigid tail unit or a folding tail unit