DE102017105519B4 - Missile approach warning system - Google Patents

Abstract

A missile approach warning system for an aircraft having at least one camera (1) for detecting at least one missile which has a structure (2) and at least one camera component (3) arranged as a detector in the structure (2), wherein: a) at least one vibration absorber (4, 4 ', 4 ") in the region of the at least one camera component (3) is arranged, wherein the at least one vibration absorber (4, 4', 4") comprises a support member (4a) on which a spring element (4c) with a damping mass (4d) is arranged, and wherein the absorber mass (4d) on the spring element (4c) slidably disposed and fixable in a certain position; and / orb) the structure (2) of the camera (1) is provided with a fastening device (9) for attachment to a structure of the aircraft, wherein the fastening device (9) comprises a first part (10) which is integral with the structure (2). the camera (1) is connected and a second part (11) which is designed for connection to the structure of the aircraft, and wherein between the first part (10) of the fastening device (9) and the second part (11) of the fastening device (9) at least one vibration damper (12) is present, which is designed as a metal or wire mesh or as an elastomer, wherein the fastening means (9) as a mounting flange with an inner metal ring as the first part (10) and an outer metal ring as a second part ( 11), and wherein the outer diameter of the inner metal ring is smaller than the inner diameter of the outer metal ring.

Description

The invention relates to a missile approach warning system with at least one camera for detecting at least one missile.

Missile approach warning systems or missile approach warning systems for military combat aircraft or civil aircraft have a plurality, in particular, for example, six cameras, preferably thermal imaging cameras for detecting approaching missiles and a processor unit for processing the camera data. Such systems are subject to high demands with regard to the optical lines of sight of the individual cameras and with regard to the temperature application range.

In aircraft, especially fighter jets, high vibration or acceleration loads occur, which result in either damage to parts or components of the cameras or requirements regarding the lines of sight can no longer be met. In order to provide an all-round monitoring of the aircraft, the cameras are arranged in different positions and, for example, directed forward, backward and downward. Cameras can also be arranged in the area of the engines or the cannons. Here are particularly strong vibrations and vibrations that affect the camera and its components. Particularly sensitive is the sensor or detector of the cameras in this regard. It is also very unfavorable if the natural resonance frequency of the cameras is in the range of the excitation frequency through the aircraft. As a result, the induced vibrations or accelerations can be multiplied so that a resonance catastrophe occurs.

To make matters worse, such cameras must have a compact design, since in aviation, the available space is usually very limited. A use of thicker or stronger housing walls or corresponding stiffening is thus often not considered in the cameras.

In the WO 2006/116460 A2 is a system for damping and / or isolating vibrations of a mass specified. The system comprises a housing, a shaft, a housing magnet and a wave magnet. The housing has an inner surface that defines a passageway. The shaft is disposed in the passage of the housing and configured to move axially therein. The shaft has an outer surface. The housing magnet is coupled to the housing inner surface. The shaft magnet is coupled to the shaft outer surface and is aligned with the housing magnet and configured to repel the housing magnet.

When in the WO 2007/003345 A1 The device for connecting a component to a structural unit is provided by a vibration device for absorbing shocks or vibrations. It is excited by vibrations or vibrations around a first point located at or near a natural vibration node. The component is rotatably mounted in the first point relative to the oscillator. An attenuator has an action component lying in the direction of movement of the first point at fundamental, and serves to attenuate a fundamental. An optional additional classic absorber is tuned to the fundamental vibration of the vibrating device.

Proceeding from this, the present invention has the object to improve a missile approach warning system of the type mentioned, in particular from the outside introduced high acceleration and / or vibration loads can act on the cameras, without causing damage to the camera or its components and without affecting the optical line of sight of the cameras.

1. a) wenigstens ein Schwingungstilger im Bereich der wenigstens einen Kamerakomponente angeordnet ist; und/oder
2. b) die Struktur der Kamera mit einer Befestigungseinrichtung zur Befestigung an einer Struktur des Flugzeugs versehen ist, wobei die Befestigungseinrichtung ein erstes Teil, welches mit der Struktur der Kamera verbunden ist und ein zweites Teil, welches zur insbesondere lösbaren Verbindung mit der Struktur des Flugzeugs ausgelegt ist, aufweist, wobei zwischen dem ersten Teil der Befestigungseinrichtung und dem zweiten Teil der Befestigungseinrichtung wenigstens ein Schwingungsdämpfer vorhanden ist, welcher insbesondere dazu ausgelegt ist, einen Eintrag von mechanischen Schwingungen oder Vibrationen von dem zweiten Teil auf das erste Teil zumindest annähernd zu verhindern oder zu dämpfen.

This object is achieved by a missile approach warning system for an aircraft with at least one camera for detecting at least one missile, which has a structure and at least one camera component arranged in the structure, wherein:

1. a) at least one vibration absorber in the region of the at least one camera component is arranged; and or
2. b) the structure of the camera is provided with a fastening device for attachment to a structure of the aircraft, wherein the fastening device, a first part, which is connected to the structure of the camera and a second part which is designed for particular detachable connection with the structure of the aircraft wherein at least one vibration damper is present between the first part of the fastening device and the second part of the fastening device, which is designed in particular to prevent or at least approximately prevent an entry of mechanical vibrations or vibrations from the second part to the first part dampen.

By using the vibration absorber on the detector and / or the vibration damper higher loads can be introduced into the camera, without causing damage to the Camera or its components or the detector comes. The reduced loads on the detector also reduces the tilt of the line of sight under vibration excitation. Also, reducing the load introduced into the camera increases the mean time between failures (MTBF). Thus, at least one means for the reduction of externally introduced mechanical vibrations or vibrations acting on the camera and / or its components is provided.

A vibration damper is a system for damping mechanical vibrations (vibrations, vibrations, shocks or acceleration). Here, an attempt is made to convert kinetic energy into heat energy. As a vibration damper (also called Tilgerpendel) special types of vibration dampers are called. Vibration absorbers are not attached between two objects, but only at one. The natural frequency of the absorber is tuned to the resonant frequency of the object to be eliminated. At this frequency, the object subsequently performs only minor movements.

It is advantageous if a plurality of vibration absorbers, in particular two, preferably three vibration absorbers are arranged around the at least one camera component. Several vibration absorbers may be arranged at regular intervals around the at least one camera component.

The at least one vibration absorber comprises a carrier element, on which a spring element with an absorber mass is arranged.

The vibration absorber can thus consist of a base plate on which a spring element or an elastic element is attached, which is provided with a damping mass or flywheel. This results in an excitation friction damping and thus vibration energy is converted into heat energy, resulting in a reduction of the vibration power to the other components of the camera.

The spring element may be designed as a wire rope with several strands or as an elastomer.

The wire rope can have several strands, in particular seven strands each with 19 individual strands, with which the friction damping can be achieved. The wire ropes can be glued into the base plate, for example. Furthermore, the spring element can also be designed as an elastomer. As a result, an increased friction damping can be achieved. It is an internal material damping, in which the polymer chains of the elastomer can slide up and down.

The absorber mass is slidably mounted on the spring element and can be fixed in a specific position.

By this measure, the natural frequency of the vibration absorber can be adjusted. This is done - similar to, for example, a guitar string or derglerichen - on the clamping length. If the absorber mass continues to move upwards, i. pushed in the direction away from the base plate, the frequency is lower, it is moved down towards the base plate, the frequency increases. Thus, the at least one vibration absorber can advantageously be set to the resonance frequency of the camera or of the system. For this purpose, the absorber mass may have a recess for receiving the spring element, wherein the clamping takes place for example by means of a screw or the like through a screw hole.

The absorber mass may comprise steel or tungsten.

In order to achieve the highest possible erosion effect, a high mass may be provided, for example using steel or tungsten.

A natural frequency of the at least one vibration absorber can be tuned to a resonance frequency of the at least one camera component or the structure of the camera to be eliminated.

The at least one camera component is a detector or sensor, and may in particular be an infrared detector, CCD or CMOS detector. Of course, other camera components, such as optical components are protected.

It is thus proposed to couple one or more vibration absorbers consisting of a damping mass and a spring element, in particular a wire rope or an elastomer with a camera component, in particular a detector. As a result of the absorber masses oscillating in opposite phase to the external vibrational excitation, resonance peaks caused by the excitation spectrum are smoothed and thus the vibrations introduced into the detector structure are reduced.

The at least one vibration damper is designed as a metal or wire mesh or as an elastomer.

Due to the friction, the introduced kinetic energy or vibration energy is converted into thermal energy by the metal or wire mesh or the elastomer.

The fastening device is designed as a mounting flange with an inner metal ring as the first and an outer metal ring as a second part, wherein the outer diameter of the inner metal ring is smaller than the inner diameter of the outer metal ring.

An annular metal or wire mesh may be interposed between the inner metal ring and the outer metal ring as a vibration damper.

The inner metal ring and / or the outer metal ring may be made in two parts.

As a result, the vibration damper or the metal or wire mesh between the metal rings can be secured by clamping. The inner metal ring and the outer metal ring may each have a groove for receiving the annular metal or wire mesh. The elastomer could also be clamped between the inner and outer metal rings.

It is thus a vibration damper specified, consisting of an inner and an outer metal ring with intermediate metal braid cushion. The outer ring is bolted to the structure of the platform, the inner ring to the structure of the camera. By the damping effect of the metal braid pad or the elastomer, a reduction of the excitation spectrum is achieved and thus reduces the vibrations introduced into the camera.

Advantageous embodiments and modifications of the invention will become apparent from the dependent claims.

The following is an exemplary embodiment of the invention with reference to the drawing in principle.

• 1 eine perspektivische Ansicht einer Kamera eines erfindungsgemäßen Flugkörperanflugwarnsystems bei geöffnetem Gehäuse;
• 2 eine schematische Darstellung eines Schwingungstilgers;
• 3 eine perspektivische Ansicht einer ersten Ausführungsform eines Schwingungstilgers;
• 4 eine perspektivische Ansicht einer zweiten Ausführungsform eines Schwingungstilgers;
• 5 eine perspektivische Ansicht einer Kamera eines erfindungsgemäßen Flugkörperanflugwarnsystems bei geschlossenem Gehäuse mit einem Befestigungsflansch;
• 6 eine vereinfachte Draufsicht auf den Befestigungsflansch gemäß 5; und
• 7 eine vereinfachte ausschnittsweise Schnittansicht des Befestigungsflansches an der Kamera gemäß 5.

Show it:

• 1 a perspective view of a camera of a missile approach warning system according to the invention with the housing open;
• 2 a schematic representation of a vibration absorber;
• 3 a perspective view of a first embodiment of a vibration absorber;
• 4 a perspective view of a second embodiment of a vibration absorber;
• 5 a perspective view of a camera of a missile approach warning system according to the invention with the housing closed with a mounting flange;
• 6 a simplified plan view of the mounting flange according to 5 ; and
• 7 a simplified partial sectional view of the mounting flange on the camera according to 5 ,

In the figures, functionally identical elements are provided with the same reference numerals.

In 1 is a camera 1 a missile approach warning system, not shown for an aircraft for the detection of missiles. The camera 1 has a structure 2 (For example, a housing or the like) and at least one in the structure 2 arranged, for example, as optics or detector, preferably infrared detector running, camera component 3 on. At least one, in the present embodiment 3 vibration absorber 4 are in the range of at least one camera component 3 arranged. The three vibration absorbers 4 are present at regular intervals around the at least one camera component 3 arranged (for example, circular at 120 ° intervals). Of course, this could not be the case in other embodiments. In 2 is a vibration absorber 4 Simplified simplified in detail. The vibration absorber 4 comprises a carrier element 4a on which a spring element 4c , especially in a recording 4b the carrier element 4a or the base plate, is arranged. The spring element 4c is with an absorber mass 4d Mistake. Due to the external vibration excitation oscillating antiphase absorber masses 4d are smoothed by the excitation spectrum caused resonance peaks and thus in the camera component 3 , For example, reduces the detector, initiated vibrations.

In 3 is a first embodiment of a vibration absorber 4 ' shown. The spring element 4c is here as a wire rope with several strands 5 executed. For example, seven strands of strands each having 19 individual strands can be provided. How out 3 further apparent is the absorber mass 4d on the spring element 4c arranged displaceably and displaceably and fixable in a certain position. This is shown by the absorber mass 4d a recess 6 for receiving the spring element 4c on. Furthermore, there is a recess 7 and a screw 8th present, with which the absorber mass 4d on the spring element 4c can be clamped. Corresponding other means such as a thread or the like are not shown here. The absorber mass 4d may be steel or tungsten.

In 4 is a second embodiment of a vibration absorber 4 ' shown. Here is the spring element 4c designed as an elastomer.

A natural frequency of the at least one vibration absorber 4 . 4 ' . 4 ' may be at a resonant frequency of the at least one camera component to be eliminated 3 or the structure 2 the camera 1 be coordinated.

The at least one camera component 3 may be a detector, in particular an infrared detector.

In 5 is a camera 1 a missile approach warning system, not shown, having a structure 2 , which comprises a housing shown. Alternatively or additionally, the structure 2 the camera 1 with a fastening device 9 for fixing the camera 1 be provided on a structure, not shown, of an aircraft, wherein the fastening means 9 a first part 10 which with the structure 2 the camera 1 connected and a second part 11 , which is designed for releasable connection with the structure of the aircraft, and wherein between the first part 10 the fastening device 9 and the second part 11 the fastening device 9 at least one vibration damper 12 is available.

The at least one vibration damper 12 can be designed as a metal or wire mesh or as an elastomer.

In the present embodiment, the fastening device 9 as a mounting flange with an inner metal ring as the first part 10 and an outer metal ring as the second part 11 executed, wherein the outer diameter of the inner metal ring is smaller than the inner diameter of the outer metal ring.

As a vibration damper 12 an annular metal or wire mesh is inserted between the inner metal ring and the outer metal ring.

6 shows the mounting flange in a plan view.

7 shows the fastening device 9 in a schematic side sectional view, with screws or shots are shown for screws. The inner metal ring and / or the outer metal ring may be made in two parts (not shown) to the vibration damper 12 be able to be secured by clamps. How out 7 further seen, the inner metal ring and the outer metal ring each have a groove 10a . 11a for receiving the vibration damper 12 on.

LIST OF REFERENCE NUMBERS

1

camera

2

Structure of the camera

3

camera component

4, 4 ', 4 "

vibration absorber

4a

support element

4b

Recording of the support element

4c

spring element

4d

absorber mass

5

strands

6

recess

7

Recess for screw

8th

screw

9

fastening device

10

First part

11

Second part

12

vibration

10a, 11a

groove

Claims (9)

A missile approach warning system for an aircraft having at least one camera (1) for detecting at least one missile which has a structure (2) and at least one camera component (3) arranged as a detector in the structure (2), wherein: a) at least one vibration absorber (4, 4 ', 4 ") in the region of the at least one camera component (3) is arranged, wherein the at least one vibration absorber (4, 4', 4") comprises a support element (4a), on which a spring element (4c) with a damping mass (4d) is arranged, and wherein the absorber mass (4d) on the spring element (4c) slidably disposed and fixable in a certain position; and / or b) the structure (2) of the camera (1) is provided with attachment means (9) for attachment to a structure of the aircraft, the attachment means (9) comprising a first part (10) connected to the structure (2 ) is connected to the camera (1) and a second part (11), which is designed for connection to the structure of the aircraft, and wherein between the first part (10) of the fastening device (9) and the second part (11) Fastening device (9) at least one vibration damper (12) is provided, which is designed as a metal or wire mesh or as an elastomer, wherein the fastening means (9) as a mounting flange with an inner metal ring as the first part (10) and an outer metal ring as a second Part (11) is performed, and wherein the outer diameter of the inner metal ring is smaller than the inner diameter of the outer metal ring. Missile approach warning system after Claim 1 , wherein a plurality of vibration absorbers (4, 4 ', 4 "), in particular three vibration absorbers (4, 4', 4") are arranged at equal intervals around the at least one camera component (3). Missile approach warning system after Claim 1 or 2 , wherein the spring element (4c) is designed as a wire rope with a plurality of strands (5) or as an elastomer. Missile approach warning system after Claim 1 . 2 or 3 wherein the absorber mass (4d) comprises steel or tungsten. Missile approach warning system according to one of Claims 1 to 4 in which a natural frequency of the at least one vibration absorber (4, 4 ', 4 ") is tuned to a resonance frequency of the at least one camera component (3) or the structure (2) of the camera (1) to be eliminated. Missile approach warning system according to one of Claims 1 to 5 wherein the detector is an infrared detector. Missile approach warning system according to one of Claims 1 to 6 wherein an annular metal or wire mesh is interposed between the inner metal ring and the outer metal ring as a vibration damper (12). Missile approach warning system according to one of Claims 1 to 7 , wherein the inner metal ring and / or the outer metal ring are made in two parts. Missile approach warning system after Claim 7 or 8th wherein the inner metal ring and the outer metal ring each have a groove (10a, 11a) for receiving the annular metal or wire mesh.

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