DE3141523C1 - Movable aperture for filtering out interfering emitters, for a device for optical guidance of missiles - Google Patents

Description

The invention relates to a movable diaphragm which delimits the field of view for masking out interference radiators for a device for the optical guidance of missiles with two parallel beam paths and associated radiation detectors for determining the position of the missile from the respective optical axis.

The use of such a diaphragm is already known from DE-PS 26 55 306 and causes after When the missile takes off, the area of the image plane within the steering device is covered to such an extent that that only the image area of the missile and its immediate surroundings on the radiation detector is mapped. This prevents interference radiators, which are in the field of view of the steering device get mapped onto the radiation detector. The field of view for the steering device Operating shooter is not affected by this measure, since he is constantly aiming at the target must be possible.

With steering devices which have two parallel beam paths and each associated radiation detector with different imaging ratios for a so-called "near area" and a "far area" have, between which it is switched in the course of the flight phase of the missile, are two diaphragms of the type mentioned above is required. The object of the invention is a displaceable, image field-delimiting To create aperture of the above type, which in steering devices for the optical steering of Missiles with two parallel beam paths and associated radiation detectors switch over from one area to the other without any problems and with as little equipment as possible Effort is involved.

This object is achieved by a diaphragm designed according to patent claim 1

The advantage of such a diaphragm is that the two diaphragm openings are completely synchronous be shifted within the respective image field, so that each of a diaphragm opening released Image section on one radiation detector, a corresponding image section on the other Radiation detector is clearly assigned. In the close range, this is assigned accordingly by the Radiation detector detected the image field through the diaphragm with the larger aperture on that of the Missile flare generated light spot limited; this is indicated either by one of the diameter of the Light spot causes corresponding aperture or, according to an advantageous development of the invention, by a circular disk-shaped filter element, which in the intersecting slots to be led. In the case of the latter, the knowledge is used that the intensity of the missile flare at close range is definitely greater than that of a flare or similar that was shot at a distance Disturbing radiator, so that a filter with a correspondingly low transparency causes only the Radiation of the flare provides a detectable deposit signal. In both embodiments of the diaphragm for the close range, the diaphragm opening is through the detected deflection signal of the missile tracked in the area of the image field, so that only the image area of the Missile and, depending on the design, more or less large area on the radiation detector is mapped.

As the distance between the missile and the steering device increases, however, it decreases in size Image diameter of the flare; likewise the received radiation intensity is lower.

For this reason - usually automatically after a certain period of time - the mentioned »far range« is added to switched to a smaller viewing angle and correspondingly smaller aperture. Since the Apertures for the »close range« and. the »far range« are moved synchronously with each other, the switchover takes place without a dark period, d. i.e. the picture of the missile flare is immediately visible on the radiation detector assigned to the "far range". Since with increasing distance of the missile the relative change in the image diameter of the flare and the received radiation intensity is steadily lower, can indicate a further reduction the aperture can be dispensed with. The invention is explained in part below with reference to one schematically illustrated embodiment described in more detail.

The figure shows two panel elements 1 and 2 arranged one behind the other, which by means of a not illustrated double shaft with a common pivot point 3 can be rotated independently of one another. the Diaphragm elements extend into beam paths 4 and 5

for the “near” or “far range” of the steering device. In the area of the beam path for the »close range« the screen element 1 has a vertical, relatively wide slot 1.1 and the screen element 2 a corresponding horizontal slot 2.1. Much narrower slots arranged accordingly 1.2 and 2.2 are provided in the area of the beam path 5 for the “far range”.

While rotating the diaphragm elements 1 and 2 only shifts the diaphragm opening 7 that is created, a circular disk-shaped filter element 6 is moved in the intersecting slots 1.1 and 2.1 of the “near area”. This filter element 6 consists of a holder 6.1 and a central filter disk 6.2 with low transmission. The outer diameter of the socket is slightly larger than the slot width of the two slots 1.1 and 2.1 and has a groove (not shown) in the cylindrical outer surface, in which the correspondingly thin-walled slot edges run. To introduce this screen element into the slots 1.1 and 2.1, the upper part of the slot 1.1 is enlarged beyond the diameter of the filter element 6 (rounding 1.11) and the slot 2.1 is carried out to the outer edge of the screen element 2. The diaphragm elements 1 and 2 can be made, for example, of thin sheet steel and the filter disk 6.2 of silicon. The common fulcrum 3 of the diaphragm elements 1 and 2 should advantageously be equidistant from the centers of the beam paths 4 and 5, ie from the optical axes of the “near” and “far range” and a distance of −i / T

where d is the distance between the optical axes

1 sheet of drawings

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Claims (4)

Patent claims: 1. Slidable, image field-limiting diaphragm to suppress interference radiation for a facility for the optical guidance of missiles with two parallel beam paths (4, 5) and each associated radiation detectors for determining the position of the missile from the respective optical axis, characterized by ä) two panel elements (1, 2) arranged one behind the other, around a common The axis of rotation (3) can be moved independently of one another and in each case in both beam paths (4, 5) protrude and b) two slits (1.1, 1.2, 2.1, 2.2) crossing each other in the area of the beam paths (4,5) within the diaphragm elements (l _s 2) with different slot widths so that in each beam path a diaphragm opening that can be displaced within the respective image field (6, 7) is created and the diaphragm openings have different diameters. 2. Cover according to claim 1, characterized in that the common axis of rotation (3) of the Aperture elements (1, 2) parallel and in one Distance - τ / 2 is arranged to the optical axes, where c / the Is the distance between the optical axes. 3. Aperture according to claim 1 or 2, characterized in that the aperture elements (1, 2) around two coaxially intermeshing shafts are rotatable. 4. Cover according to one of claims 1 to 3, characterized in that at least one pair of intersecting slots (1.1,1.2) serves as a guide for a circular disk-shaped filter element (6). 40