DE10218169B4 - Antenna elements for a missile - Google Patents

Abstract

Antenna elements for the UHF and VHF range for antennas of a missile with tail elements, wherein the tail elements (L) are of dielectric material and the antenna elements (A) with a feed (E) structurally integrated in these tail elements (L) and are formed in that they emit broadband in the direction of flight, characterized in that the antenna elements (A) are widening slot radiators which are bisected along their axis of symmetry and use the missile (F) as electric mirror.

Description

The The invention relates to antenna elements for the UHF and VHF range for antennas a missile with tail elements, wherein the tail elements of dielectric Material are and the antenna elements in these tail elements integrated and are designed such that they are directed broadband radiate in the direction of flight.

to clarification, clearing up of something and bearing in the VHF frequency range are currently due to their used relatively compact structure spiral antennas. At low frequencies (<1 GHz) and as possible However, these antennas have a greatly reduced volume Antenna gain on, or are not of their dimensions to Integration in the missile suitable.

at missiles with a length dimension in the order of magnitude the wavelength used occurs within the low frequency ranges (<1 GHz) the problem on that directionally radiating antennas due to their aperture requirements no longer within the missile structure are to be arranged, or achieved no directional antenna behavior can be.

The US 6 097 343 A describes an antenna element for the UHF and VHF range for use as an antenna of a missile with tail elements. These consist at least partially of the electrical material and are integrated into the tail elements. The broadband radiation takes place in the direction of flight.

The EP 0 341 772 A1 also relates to a missile with integrated in the tail antenna elements.

Out DE 195 43 321 A1 For example, a missile with antenna elements integrated into dielectric wing elements is known for communication purposes. For example, from the DE 197 15 206 A1 It is also known to arrange planar antennas on dielectric substrates.

The resulting planar structures (eg patch antennas) have but not the for a bearing necessary directivity. In addition, this one used in the two sites mentioned antenna type on the for the Application available standing missiles can not be arranged so that a radiation in the direction of flight is reached. Also the arrangement in an array - if the needed area to disposal would stand, as in the first reference, does not change this fact, because at a beam deflection more than 60 ° from the surface normal a significant Profit reduction occurs.

One further point, the patch elements as unsuitable for the application appear according to the invention leaves, is the required broadband, which with 1:20 with the described Antennas can not be reached. This type of antenna is thus in principle for the planned bearing in flight direction unsuitable.

antennas with an externally similar construction are also used in the field of communication technology (eg aerodynamic shaped "blade antennas" in rail vehicles) used. The essential difference to these structures exists in the physical separation of radome and antenna and in the The fact that these antennas radiate undirected.

It the object of the invention is to provide an antenna arrangement at the antenna elements despite the spatial and mechanical limitations through the missile have the required behavior, ie in particular in the direction of flight radiate directed broadband.

According to the invention This is achieved by the features listed in claim 1.

It So if the tail of the missile is used, in order to broadband in this area in the direction of flight acting Antenna structures to integrate, without the mechanical functionality of the tail area disturb.

details The invention results from the subclaims and the description, in the reference to the drawing an embodiment is discussed.

The Figure shows a possible execution the "fin antenna" according to the invention. she consists from a dielectric tail L, into which the antenna structure A embedded with the feed E or applied to its surface is. Due to the low frequencies, the used effect Dielectric only to a small extent on the properties of the antenna elements. So there is one structural integration of antenna and Ru the before (positive and non-positive connection), wherein further protective measures for the Antenna in the form of a radome omitted.

The antenna element A used is based on a widening slot radiator, which is bisected along its axis of symmetry. In this case, the entire missile F is included in the antenna concept. This type of antenna is also described in the literature as a Vivaldi element. New in this context is the idea to halve the antenna element and the missile despite his to use as an electrical mirror compared to the wavelength of small dimensions.

Different as in traditional antenna concepts where the carrier is large in relation to the wavelength and thus can be considered as a metallic level is added the concept of the invention thus the structure of the missile F Part of the antenna.

The novel arrangement of the antenna elements A in the region of the rudder L, both the aperture and the distance of the phase centers of the individual elements is maximized, but no additional volume for the antennas is needed. If the evaluation of the received signals with the classical amplitude or phase monopulse method, the requirements of the detection channels are kept low by the proposed arrangement. Thus, an extension of the frequency range for bearing and reconnaissance to lower frequencies (eg Z. 100 MHz) is possible. In order to enable a bearing in azimuth and elevation for all polarizations, a total of 4 antenna elements are necessary, which are each pairwise orthogonally polarized. Such an arrangement is in principle already in DE 1168513 A In contrast, the antenna system according to the invention is oriented at an angle of 45 °. This orientation is essential for the intended application, since only so the required polarization agility, namely linear horizontal and linear vertical polarization and circular left- and right-handed polarization can be achieved in the bearing.

• – Peilung und Aufklärung in Flugrichtung,
• – eine Erweiterung des Frequenzbereiches zur Peilung und Aufklärung zu tieferen Frequenzen (z. Z. 100 MHz),
• – eine Reduzierung des von den Antennen benötigten Volumens,
• – eine maximale Antennenapertur bei maximalem Abstand der Phasenzentren, und
• – die strukturelle Integration der Antenne in den Flugkörper (Form- und Kraftschluß).

In summary, therefore, the following advantages result from the structure according to the invention:

• - Bearing and reconnaissance in the direction of flight,
• - an extension of the frequency range for bearing and reconnaissance to lower frequencies (eg 100 MHz),
• A reduction of the volume required by the antennas,
• A maximum antenna aperture at maximum distance of the phase centers, and
• - The structural integration of the antenna in the missile (form and adhesion).

Claims (2)

Antenna elements for the UHF and VHF range for antennas of a missile with tail elements, wherein the tail elements (L) are of dielectric material and the antenna elements (A) with a feed (E) structurally integrated in these tail elements (L) and are formed in that they emit broadband in the direction of flight, characterized in that the antenna elements (A) are widening slot radiators which are bisected along their axis of symmetry and use the missile (F) as electric mirror. Antenna elements according to Claim 1, characterized that on a missile with four control elements a total of four antenna elements (A) or in each case a tail element are arranged, each in pairs are polarized orthogonally, the antenna system aligned at an angle of 45 ° is.